Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/64—Reversing fan flow
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/64—Reversing fan flow
  • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/64—Reversing fan flow
  • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
  • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/76—Control or regulation of thrust reversers
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/76—Control or regulation of thrust reversers
  • F02K1/763—Control or regulation of thrust reversers with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2260/00—Function
  • F05D2260/50—Kinematic linkage, i.e. transmission of position
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2260/00—Function
  • F05D2260/50—Kinematic linkage, i.e. transmission of position
  • F05D2260/56—Kinematic linkage, i.e. transmission of position using cams or eccentrics
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

• the present invention relates to a thrust reverser with grids for a turbojet engine nacelle, and a turbojet engine nacelle equipped with such thrust reverser.
• Aircraft turbojet engines arranged along a longitudinal axis, inserted in a nacelle, receive fresh air from the front side, and reject the back side hot gases from the combustion of the fuel delivering thrust.
• fan blades disposed around the engine generate a large secondary flow of cold air along an annular vein passing between the engine and the nacelle, which adds a high thrust.
• Some nacelles include a thrust reversal system which at least partially closes the annular cold air duct, and reject the secondary flow radially outwardly by directing it forward to generate an inverted braking thrust. the aircraft.
• a known type of thrust reverser grids presented in particular by the document US-A1-20160160799, comprises rear movable cowls sliding axially backwards under the effect of jacks, to open lateral air passages on the nacelle containing grids.
• the rear hoods are connected by control rods mounted on joints, describing curves in an axial plane, the thrust reversal grids driven rearward, and closure flaps of the main stream.
• the links are arranged to obtain a translation of the grids to the rear less than that of the covers, and a tilting of the flaps in the annular cold air duct which at least partially closes this vein by directing the flow radially to the outside through grids returning this flow forward.
• this type of thrust reverser comprising rods arranged below the grids, describing curves in an axial plane, occupies a relatively large volume below these grids which does not optimize the aerodynamic forms of the annular vein, as well as soundproofing panel lining.
• the present invention is intended to avoid these disadvantages of the prior art. It proposes for this purpose a thrust reverser for a turbojet engine nacelle, comprising thrust reversal grids disposed around an annular duct comprising radially outwardly a fixed front casing, comprising at least one movable cowling recoiling towards the outside.
• an advantage of this inverter is that in the closed position the grids and tilting flaps being arranged above the fixed housing, the axial length of the nacelle can be very short.
• the slide can be stored above the fixed hood which completely releases the passage of the annular vein by limiting aerodynamic losses.
• the thrust reverser according to the invention may further comprise one or more of the following features, which may be combined with one another.
• the rocker flaps and the grids are successively arranged in this order outside the fixed casing.
• the inverter comprises a slide support linked from the front side by a pivot to the grids, supporting the slides which are fixed on it, controlling the opening of a flap.
• the inverter comprises a first slide receiving in a groove a transverse axis connected to the front casing, which controls a tilting of the slide support.
• the inverter comprises a second slide receiving in a groove a transverse finger connected to the flaps, which controls a tilting of this flap.
• the two grooves form cams to easily adjust the kinematics of the movement of the flap.
• the slide support has on the rear side an annular groove section, which is in the axially closed position interposed between the front casing and an inner surface of the annular duct of the movable hood.
• the slide support has in the open position an internal passage of the flow having deflection edges of this flow. This improves the flow deflection radially outwards.
• said slide support comprises blades for directing the flow of air from said annular vein to said grids.
• each flap comprises two half-flaps sliding relative to each other. In the closed position the flap is thus much more compact.
• the inverter comprises at least one telescopic rod comprising an inner portion and an outer portion each fixed to a half-flap for guiding it.
• the inverter comprises on each side of a flap, at least one connecting rod comprising a pivoting end attached to the grids and the other pivoting end attached to the flap, to guide the flap.
• the invention also relates to a turbojet engine nacelle comprising a thrust reverser grid, equipped with an inverter comprising any of the previous characteristics.
• FIGS. 1, 2a, 2b and 3 show a thrust reverser according to the invention which is closed, respectively presented in axial section along a cutting plane passing on the side of a grid, a cutting plane passing through a slide curve, a sectional plane passing through a straight slide, and presented in perspective;
• FIGS. 7 and 8 respectively show, according to the first two section planes, this thrust reverser open at 50%;
• FIGS. 9 and 10 respectively show, according to the first two section planes, this thrust reverser open at 75%
• Figures 1, 2a, 2b and 3 show a thrust reverser of a nacelle having a main axis having a front side indicated by the arrow AV, corresponding to the direction of travel.
• the nacelle comprises an annular cold air duct receiving a flow F delimited radially outwards by a fixed front casing 2, which extends rearwardly by the inner face 6 of a movable rear cover 4.
• the movable rear cover 4 comprises on the front side, a circular rear frame 8 and a circular front frame 12, receiving flow reversal grids 10 covering the annular space formed between these two frames.
• Movable flaps each comprising a front half-flap 16 and a rear half flap 14, superimposed on one another, are arranged flat just below each grid 10.
• a telescopic rod 18 disposed in the middle of each flap has an inner portion comprising on the rear side a pivot 42 connected to the movable cover 4 (and more specifically to the rear frame 8 in the example), which is fixed to the rear half-flap 14 , and an outer part 20 sliding around the inner part, which is fixed to the front half-flap 16.
• an extension of the telescopic rod 18 makes a sliding of the two half-flaps 14, 16 one on the other.
• a connecting rod 22 On each side of the grids 10, a connecting rod 22 has a front pivot 24 fixed to the front frame 12, and a rear pivot 26 fixed on the side of the front half-flap 16.
• a slide support 30 forming a plate disposed below each grid 10 has at its front end a pivot 32 fixed to the front frame 12, and at the rear a section of annular vein 34, having a small axial length which is adjusted between the front casing 2 and the inner face 6 of the rear cover 4 to ensure aerodynamic surface continuity between them.
• seals can be arranged between the annular vein section 34, and on one side the front casing 2, and the other side the inner face 6 of the rear cover 4, to ensure in the closed position of the thrust reverser sealing the flow avoiding air passages radially outwardly of the annular vein.
• an acoustic attenuation material may be added to the section of annular vein 34, so as to contribute to absorbing acoustic vibrations in the annular vein, and to reducing noise emissions.
• a first slide connection is formed for example by a single straight slide 44 having an elongate flat shape, preferably disposed in an axial plane in the middle of each flap, between the flap and the front casing 2; this straight slide has a front end fixed to the front of the slide support 30, and a straight inner groove substantially parallel to the main axis of the nacelle.
• the front end of the outer portion 20 of the telescopic rod 18 comprises a transverse finger 46 engaged in this right groove.
• a second slide connection is formed for example by a curved slide 36 having an elongated flat shape, preferably arranged parallel to the straight slideway 44, also having its front end fixed to the front of the slide support 30.
• the curved slide 36 has an inner groove substantially parallel to the main axis of the nacelle, having a slight curvature turned towards this main axis.
• the radially outer surface of the annular duct has good aerodynamic continuity with the section of annular duct 34 ensuring continuity between the front casing 2 and the inside face 6 of the rear casing 4. No mechanism disturbs the flow of the duct. fluid in this vein.
• the thrust reverser is completely concentrated outside the front casing 2, forming a flat assembly fitted between this casing and the grids 10 arranged outside. It hardly protrudes behind the front cover 2, which allows the rear cover 4 to be very advanced.
• Figures 4, 5a, 5b and 6 show the open thrust reverser, the rear cover 4 having fully retracted under the effect of a motorization by driving the grids 10 and the half-flaps 14, 16.
• the recoil of the curved slide 36 fixed to the front frame 12, causes a sliding of the transverse axis 40 in its groove.
• the front pivoting axis of the curved slide 36 positioned above the transverse axis 40, implies a downward tilting of this curved slide, which likewise causes the slide support 30 to tilt downwards.
• the right slide 44 having the same downward tilting movement, drives the front transverse finger 46 of the telescopic rod 18, which is deployed by giving the same movement to the front and rear half-flaps 14, respectively fixed to the outer part 20 and the inner portion 18 of this rod.
• a deployment of the flaps with the annular section 34 coming close to the radially inner surface 50 of the annular vein is obtained. shutters largely closing the annular vein. The flow is deflected by the flaps radially outward, to pass through the grids 10 which direct this flow forward by generating the braking thrust.
• the rods 22 arranged on each side of the flaps by their rear pivot 26 provide a guiding of the half-flaps before 16.
• Two rods 22 are preferred, but the system could also work with a single rod.
• the slide support 30 may have different shapes. It may in particular comprise fins making a first direction of the flow radially outwards.
• Figures 7 and 8 show a decline in the movable rear cover 4 equal to 50% of the total stroke.
• the transverse axis 40 is quite far from the front pivot of the slide support 30, this support has tilted very little.
• the section of annular vein 34 has retracted with the rear cover 4, but remains close to the inner face 6 of this cover.
• the curved slideway 36 and the straight slideway 44 have, like the slideway support 30, very few tilts, the half-flaps 14, 16 remain close to the grids 10.
• Figures 9 and 10 show a retreat of the movable rear cover 4 larger, equal to 75% of the total stroke. Under the effect of the transverse axis 40 which is close to the front pivot of the slide support 30, this support has tilted a little more while following the recoil of the rear cover.
• the curved slide 36 and the right slide 44 swing in the same way, but the right shape of this straight slide causes a slight lowering of the transverse finger 46 connected to the telescopic rod 18.
• the half-flaps 14, 16 have tilted little.
• Figures 11 and 12 show a decline in the movable rear cover 4 larger, equal to 90% of the total stroke. Under the effect of the transverse axis 40 which arrives near the front pivot of the slide support 30, this support has rocked strongly.
• Curved slide 36 and straight slide 44 swing in the same way.
• the right shape of the right slide 44 causes a greater lowering of the transverse finger 46 connected to the telescopic rod 18.
• the half-flaps 14, 16 rock strongly.
• FIG. 13 shows the rear end of the front casing 2 having a fixed rear deflection edge 60 rotated radially outwards, which helps guide the flow radially outwardly in the open position of the thrust reverser.
• the slide support 30 also has in its internal passage of the flow, a movable deflection edge 62 having a curved shape towards the axis of the nacelle, which also helps guide this flow radially outwardly in the open position.
• this slide support 30 may comprise vanes or fins for appropriately directing the flow F of the annular vein towards the grids 10.
• the straight slideway 44 could be replaced by a rack cooperating with the transverse front finger 46 of the telescopic rod 18.

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• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Wind Motors (AREA)

Applications Claiming Priority (2)

Publications (2)

Family

ID=60020175

Family Applications (1)

Country Status (6)

Families Citing this family (4)

Family Cites Families (23)

• 2017
  • 2017-08-31 FR FR1758044A patent/FR3070439B1/fr not_active Expired - Fee Related
• 2018
  • 2018-08-30 WO PCT/FR2018/052133 patent/WO2019043343A1/fr not_active Ceased
  • 2018-08-30 EP EP18773536.0A patent/EP3676486B1/de active Active
  • 2018-08-30 CN CN201880056215.1A patent/CN111065810B/zh active Active
  • 2018-08-30 RU RU2020109920A patent/RU2735974C1/ru active
• 2020
  • 2020-03-02 US US16/806,251 patent/US11293377B2/en active Active

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